US4951461A - Power turbine support arrangement - Google Patents

Power turbine support arrangement Download PDF

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Publication number
US4951461A
US4951461A US07/325,728 US32572889A US4951461A US 4951461 A US4951461 A US 4951461A US 32572889 A US32572889 A US 32572889A US 4951461 A US4951461 A US 4951461A
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US
United States
Prior art keywords
rotor
annular
rotors
static structure
bearing means
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
US07/325,728
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English (en)
Inventor
Lawrence Butler
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General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Assigned to GENERAL ELECTRIC COMPANY, A CORP. OF NY reassignment GENERAL ELECTRIC COMPANY, A CORP. OF NY ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: BUTLER, LAWRENCE
Priority to US07/325,728 priority Critical patent/US4951461A/en
Priority to CA002007152A priority patent/CA2007152A1/en
Priority to FR9002879A priority patent/FR2644515A1/fr
Priority to JP2061350A priority patent/JPH02267325A/ja
Priority to GB9005867A priority patent/GB2229498B/en
Priority to DE4008432A priority patent/DE4008432A1/de
Priority to IT19733A priority patent/IT1239397B/it
Publication of US4951461A publication Critical patent/US4951461A/en
Application granted granted Critical
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/072—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with counter-rotating, e.g. fan rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This invention relates generally to gas turbine engines and, more, particularly, to a coupling arrangement for supporting the power turbine of an unducted fan engine on a static structure.
  • Gas turbine engines such as the type used in aircraft generally include a compressor, a combustor, and a high pressure turbine in serial flow relationship. Air entering the engine is compressed by the compressor and then mixed with fuel and ignited to form a high energy gas stream. The gas stream passes through the high pressure turbine where some of the combustion energy is extracted to drive the compressor.
  • Turboprop and turbofan engines used for aircraft propulsion also commonly include a second turbine, known as a power turbine, located downstream (aft) of the high pressure turbine. The power turbine extracts energy from the gas stream to drive a plurality of propeller or fan blades which provide the propulsive force to move an aircraft.
  • the Johnson patent application discloses first and second rotors coaxially positioned about a static structure wherein the first rotor is rotatably coupled to the static structure by a first set of roller-element bearings, and the second rotor is rotatably coupled to the static structure by second set of roller element bearings.
  • a disadvantage of supporting both rotors directly on the static structure is that axial bending of the static structure may cause turbine blades in one annular array to deflect, or, at worst, collide with counter-rotating turbine blades in an adjacent annular array. Such deflections may occur when the static structure experiences bending forces from the propulsor blades while also supporting the weight of the rotors. As an aircraft undergoes maneuvers or is subjected to external forces, the static structure is subjected to bending moments resulting in deflections of the rotor supports.
  • adjacent arrays of turbine blades may have different axes of rotation and collide with each other. Because such a collision may cause serious damage to the power turbine, it is desirable to provide a power turbine for an unducted fan type engine in which the adjacent arrays of turbine blades are not subject to deflections of this type.
  • the engine mounts coupling the engines to the aircraft are attached to each engine forward of the power turbine section in order to avoid interferences with the propulsor blades.
  • Part of the static structure is suspended rearward of the engine mounts centrally through the power turbine section in order to support the rotors of that section.
  • a disadvantage of supporting each rotor directly on the static structure is that the static structure must be of an extended length in order to separately support each rotor. In order to provide a relatively rigid, non-deflecting support for this lengthy suspended configuration the overall size and mass of the stator must be relatively large. The corresponding weight increase directly affects aircraft fuel efficiency. If the rotors could be supported in a manner which would permit the length of the static structure to be reduced, the weight of the engine could also be reduced and the fuel efficiency of the aircraft further increased.
  • the present invention is incorporated in the power turbine section of a gas turbine engine comprising a stator, first and second rotors, and first and second bearing means.
  • the first and second rotors are coaxially positioned about a longitudinal axis of the stator.
  • An annular gas flowpath is disposed about the longitudinal axis between the first and second rotors.
  • Each rotor is coupled to a plurality of annular arrays of turbine blades arranged circumferentially about the rotor and extending into the gas flowpath such that gas flow through the flowpath causes each of the rotors to rotate.
  • Each array of turbine blades attached to the first rotor is coaxial with and adjacent to an array of turbine blades attached to the second rotor forming alternating interdigitated annular arrays of blades for each rotor.
  • First bearing means are interposed between the first rotor and the stator to rotatably secure the first rotor to the stator.
  • Second bearing means are interposed between the first and second rotors to rotatably secure the second rotor to the first rotor. Since the second rotor is secured to the first rotor, both rotors maintain a substantially common axis of rotation notwithstanding any stator deflections with respect to the longitudinal axis.
  • both the first and second rotors lies along the longitudinal axis aft of the first bearing means.
  • the rotors are supported in a cantilever fashion aft of the first bearing means. Since the portion of the stator extending aft of the first bearing means is not load supporting, its strength and corresponding length and mass need not be as great as the portion of the stator forward of the first bearing means. This allows a reduction in weight and improves fuel efficiency.
  • FIG. 1 is a perspective view of an unducted fan type gas-turbine engine
  • FIG. 2 is a side elevation view, in cross-section, of a portion of the power turbine section in an unducted fan type gas-turbine engine constructed in accordance with the present invention.
  • FIGS. 1 and 2 illustrate an unducted fan jet engine 20 arranged substantially concentrically about a central longitudinal engine axis 58.
  • the engine includes forward and aft counterrotating fan or propulsor blades 22 and 24 disposed radially outward from a power turbine section 25.
  • the power turbine section 25 includes first and second counterrotating rotors 26 and 28 each coupled to a plurality of annular arrays of counterrotating turbine blades 30 and 32.
  • Forward and aft fan blades 22 and 24 are coupled to the first and second rotors 26 and 28, respectively, and rotate therewith.
  • the counterrotating turbine blades 30 and 32 lie in an annular gas flowpath 42 defined by the first and second rotors 26 and 28. Air passing through the engine 20 is compressed and heated to form a high energy (high pressure/high temperature) gas stream indicated generally by arrow 44. Gas stream 44 expands through the flowpath 42 reacting against the blades 30 and 32 to rotate the rotors 26 and 28 which in turn drive the counterrotating fan blades 22 and 24, respectively. A cone 49 located aft of and secured to the second rotor 28 provides the proper air flow characteristics of the gas stream 44 as it exits the engine 20.
  • the rotor 26 includes a forward structural support portion 50 concentrically positioned about an aft portion of a central static structure 52.
  • the forward portion 50 is rotatably secured to the static structure 52 by way of rolling element type bearings including an annular thrust bearing 54 and two annular roller bearings 56 interposed between the static structure 52 and the forward portion 50.
  • First rotor 26 is adjacent static structure 52, aligned along longitudinal axis 58 and the second rotor 28 is concentrically positioned about the first rotor 26.
  • the second rotor 28 is rotatably secured to an aft portion 60 of the first rotor 26 by way of another annular thrust bearing 62 and two annular roller bearings 64 interposed between the rotors.
  • the entire weight of the power turbine section 25 is supported by the static structure 52 through the bearings 54 and 56. Propulsive thrust from the power turbine section 25 is transferred to the static structure 52 through the forward most thrust bearing 54. It is noted that the reaction of gyro-moments of the two counterrotating rotors is reacted internally, i.e., due to the counter rotation, the positive moment of the forward rotor is reacted by the negative moment of the aft rotor through the bearings that connect the two. Therefore, there is practically zero net gyro moment transferred through the engine mounts to the air frame thus allowing lighter and softer mounts to be used.
  • a further advantage of rotatably coupling the second rotor 28 to the first rotor 26 is that the rotor 32 need not be coupled directly to the static structure 52 for support purposes. If the stator structure 52 were extended rearward to support the second rotor 28, its size and mass would have to be increased along the axis 58 in order to support the second rotor 28 and withstand bending moments. However, the stator structure 52 may nevertheless be extended to or beyond the aft portion 60 of rotor 26 for nonstructural reasons such as the housing of control lines which communicate with the aft portion of the engine. Such an extended housing structure need not be as strong or massive as would be necessary for the direct support of a second rotor. By supporting the entire power turbine 25 at a forward position of the turbine in the aforedescribed manner the overall weight of the engine 20 may be reduced.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US07/325,728 1989-03-20 1989-03-20 Power turbine support arrangement Expired - Fee Related US4951461A (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
US07/325,728 US4951461A (en) 1989-03-20 1989-03-20 Power turbine support arrangement
CA002007152A CA2007152A1 (en) 1989-03-20 1990-01-04 Power turbine support arrangement
FR9002879A FR2644515A1 (fr) 1989-03-20 1990-03-07 Montage de turbine de puissance
JP2061350A JPH02267325A (ja) 1989-03-20 1990-03-14 パワータービン支持構造
GB9005867A GB2229498B (en) 1989-03-20 1990-03-15 Power turbine section of a gas turbine engine
DE4008432A DE4008432A1 (de) 1989-03-20 1990-03-16 Halterungsanordnung fuer eine leistungsturbine
IT19733A IT1239397B (it) 1989-03-20 1990-03-20 Complesso di sostegno per turbina di potenza

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US07/325,728 US4951461A (en) 1989-03-20 1989-03-20 Power turbine support arrangement

Publications (1)

Publication Number Publication Date
US4951461A true US4951461A (en) 1990-08-28

Family

ID=23269175

Family Applications (1)

Application Number Title Priority Date Filing Date
US07/325,728 Expired - Fee Related US4951461A (en) 1989-03-20 1989-03-20 Power turbine support arrangement

Country Status (7)

Country Link
US (1) US4951461A (enrdf_load_stackoverflow)
JP (1) JPH02267325A (enrdf_load_stackoverflow)
CA (1) CA2007152A1 (enrdf_load_stackoverflow)
DE (1) DE4008432A1 (enrdf_load_stackoverflow)
FR (1) FR2644515A1 (enrdf_load_stackoverflow)
GB (1) GB2229498B (enrdf_load_stackoverflow)
IT (1) IT1239397B (enrdf_load_stackoverflow)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5186609A (en) * 1990-12-20 1993-02-16 Honda Giken Kogyo Kabushiki Kaisha Contrarotating propeller type propulsion system
US5307622A (en) * 1993-08-02 1994-05-03 General Electric Company Counterrotating turbine support assembly
US6619030B1 (en) 2002-03-01 2003-09-16 General Electric Company Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors
US6732502B2 (en) 2002-03-01 2004-05-11 General Electric Company Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor
US20060120854A1 (en) * 2004-12-08 2006-06-08 Wakeman Thomas G Gas turbine engine assembly and method of assembling same
US7063505B2 (en) 2003-02-07 2006-06-20 General Electric Company Gas turbine engine frame having struts connected to rings with morse pins
WO2010092094A1 (fr) * 2009-02-13 2010-08-19 Snecma Systeme d'helices contrarotatives a encombrement reduit
US20130098066A1 (en) * 2011-10-21 2013-04-25 Snecma Turbine engine comprising a contrarotating propeller receiver supported by a structural casing attached to the intermediate housing
US8863491B2 (en) 2012-01-31 2014-10-21 United Technologies Corporation Gas turbine engine shaft bearing configuration
US9038366B2 (en) 2012-01-31 2015-05-26 United Technologies Corporation LPC flowpath shape with gas turbine engine shaft bearing configuration
US9068629B2 (en) 2011-04-27 2015-06-30 United Technologies Corporation Fan drive planetary gear system integrated carrier and torque frame
US9784181B2 (en) 2009-11-20 2017-10-10 United Technologies Corporation Gas turbine engine architecture with low pressure compressor hub between high and low rotor thrust bearings
US10400629B2 (en) 2012-01-31 2019-09-03 United Technologies Corporation Gas turbine engine shaft bearing configuration
US10641205B2 (en) * 2013-06-07 2020-05-05 United Technologies Corporation Exhaust stream mixer
CN111706432A (zh) * 2020-05-28 2020-09-25 中国航发湖南动力机械研究所 新型桨扇发动机及具有其的推进装置

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8752394B2 (en) * 2010-03-15 2014-06-17 Rolls-Royce Corporation Determining fan parameters through pressure monitoring

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3524318A (en) * 1967-12-14 1970-08-18 Snecma Gas turbine power plants having axialflow compressors incorporating contrarotating rotors
US4621978A (en) * 1984-12-03 1986-11-11 General Electric Company Counterrotating power turbine
US4738591A (en) * 1986-09-09 1988-04-19 General Electric Company Blade pitch varying mechanism
US4758129A (en) * 1985-05-31 1988-07-19 General Electric Company Power frame
US4790133A (en) * 1986-08-29 1988-12-13 General Electric Company High bypass ratio counterrotating turbofan engine

Family Cites Families (10)

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US2541098A (en) * 1948-06-14 1951-02-13 Westinghouse Electric Corp Gas turbine propeller apparatus
GB774502A (en) * 1954-07-01 1957-05-08 Power Jets Res & Dev Ltd Gas turbine plant
US2977160A (en) * 1958-12-22 1961-03-28 Orenda Engines Ltd Support structure for gas turbine bearings
NL8303401A (nl) * 1982-11-01 1984-06-01 Gen Electric Aandrijfturbine voor tegengesteld draaiende propellers.
US4907944A (en) * 1984-10-01 1990-03-13 General Electric Company Turbomachinery blade mounting arrangement
CA1262409A (en) * 1985-05-01 1989-10-24 Kenneth Odell Johnson Counter rotation power turbine
US4817382A (en) * 1985-12-31 1989-04-04 The Boeing Company Turboprop propulsion apparatus
GB2192237B (en) * 1986-07-02 1990-05-16 Rolls Royce Plc Gas turbine engine power turbine
US4738590A (en) * 1986-09-09 1988-04-19 General Electric Company Blade pitch varying mechanism
GB2207191B (en) * 1987-07-06 1992-03-04 Gen Electric Gas turbine engine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3524318A (en) * 1967-12-14 1970-08-18 Snecma Gas turbine power plants having axialflow compressors incorporating contrarotating rotors
US4621978A (en) * 1984-12-03 1986-11-11 General Electric Company Counterrotating power turbine
US4758129A (en) * 1985-05-31 1988-07-19 General Electric Company Power frame
US4790133A (en) * 1986-08-29 1988-12-13 General Electric Company High bypass ratio counterrotating turbofan engine
US4738591A (en) * 1986-09-09 1988-04-19 General Electric Company Blade pitch varying mechanism

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5186609A (en) * 1990-12-20 1993-02-16 Honda Giken Kogyo Kabushiki Kaisha Contrarotating propeller type propulsion system
US5307622A (en) * 1993-08-02 1994-05-03 General Electric Company Counterrotating turbine support assembly
US6619030B1 (en) 2002-03-01 2003-09-16 General Electric Company Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors
US6732502B2 (en) 2002-03-01 2004-05-11 General Electric Company Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor
US7063505B2 (en) 2003-02-07 2006-06-20 General Electric Company Gas turbine engine frame having struts connected to rings with morse pins
US20060120854A1 (en) * 2004-12-08 2006-06-08 Wakeman Thomas G Gas turbine engine assembly and method of assembling same
WO2010092094A1 (fr) * 2009-02-13 2010-08-19 Snecma Systeme d'helices contrarotatives a encombrement reduit
FR2942203A1 (fr) * 2009-02-13 2010-08-20 Snecma Systeme d'helices contrarotatives a encombrement reduit
CN102317598A (zh) * 2009-02-13 2012-01-11 斯奈克玛 紧凑型对转螺旋桨系统
CN102317598B (zh) * 2009-02-13 2014-11-19 斯奈克玛 紧凑型对转螺旋桨系统
US9057326B2 (en) 2009-02-13 2015-06-16 Snecma System of compact contra-rotating propellers
US9784181B2 (en) 2009-11-20 2017-10-10 United Technologies Corporation Gas turbine engine architecture with low pressure compressor hub between high and low rotor thrust bearings
US9068629B2 (en) 2011-04-27 2015-06-30 United Technologies Corporation Fan drive planetary gear system integrated carrier and torque frame
US20130098066A1 (en) * 2011-10-21 2013-04-25 Snecma Turbine engine comprising a contrarotating propeller receiver supported by a structural casing attached to the intermediate housing
US9217391B2 (en) * 2011-10-21 2015-12-22 Snecma Turbine engine comprising a contrarotating propeller receiver supported by a structural casing attached to the intermediate housing
US9038366B2 (en) 2012-01-31 2015-05-26 United Technologies Corporation LPC flowpath shape with gas turbine engine shaft bearing configuration
US9194329B2 (en) 2012-01-31 2015-11-24 United Technologies Corporation Gas turbine engine shaft bearing configuration
US8863491B2 (en) 2012-01-31 2014-10-21 United Technologies Corporation Gas turbine engine shaft bearing configuration
US10215094B2 (en) 2012-01-31 2019-02-26 United Technologies Corporation Gas turbine engine shaft bearing configuration
US10400629B2 (en) 2012-01-31 2019-09-03 United Technologies Corporation Gas turbine engine shaft bearing configuration
US11149689B2 (en) 2012-01-31 2021-10-19 Raytheon Technologies Corporation Gas turbine engine shaft bearing configuration
US11486269B2 (en) 2012-01-31 2022-11-01 Raytheon Technologies Corporation Gas turbine engine shaft bearing configuration
US11566586B2 (en) 2012-01-31 2023-01-31 Raytheon Technologies Corporation Gas turbine engine shaft bearing configuration
US10641205B2 (en) * 2013-06-07 2020-05-05 United Technologies Corporation Exhaust stream mixer
CN111706432A (zh) * 2020-05-28 2020-09-25 中国航发湖南动力机械研究所 新型桨扇发动机及具有其的推进装置

Also Published As

Publication number Publication date
JPH02267325A (ja) 1990-11-01
GB9005867D0 (en) 1990-05-09
GB2229498B (en) 1993-08-04
IT1239397B (it) 1993-10-20
CA2007152A1 (en) 1990-09-20
DE4008432C2 (enrdf_load_stackoverflow) 1992-04-23
FR2644515A1 (fr) 1990-09-21
DE4008432A1 (de) 1990-09-27
GB2229498A (en) 1990-09-26
IT9019733A0 (it) 1990-03-20
IT9019733A1 (it) 1991-09-20

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